Rocket launching device



Aug. 9, 1949., A. B. MEINEI.

ROCKET LAUNCHING DEVICE Filed Jan. 20L 1947 Aden-E1. ME'iILEl Patented Aug. 9, 1949 UNITED S Secretary of War United States of America as represented by the Application January 20, 1947, Serial No. 723,159

7 Claims.

This invention relates to a new and useful improvement in rocket launchers and is designed more particularly to Aprovide a cl'osed breech launcher for use under Iconditions which prevent use of an open breech launcher, as in tank turrets. The closed breech launcher has certain recognized advantages over the open breech type, such as increased range, which would make its use desirable under conditions in which an open breech type could be used, While the character and functioning :of the breech mechanism required forsuch closed breech launchers present in'a'ny problems requiring satisfactory solution for efficient operation of the launcher, this invention is not relevant to such matters, as it concerns only the structure of the launcher tube, it being assumed that the improved tube is equipped with a satisfactory breech mechanism. Since the functioning of closed breech and open breech launchers are quite dissimilar, this invention is concerned with satisfactorily solving the problems involved in the operation of closed breech launchers.

Extensive investigation and experimental work have been carried on to overcome the detrimental effect of the gases of the propellant which in this type of launcher have no breech escape and must be evacuated from the launcher tube forwardly of the breech. The particularly novel and useful features of the improved tube of this invention are the ychannel rails on which the rocket moves through the tube, the muzzle-brake comprising gas discharge ports, and a gas obturating ring, and the peculiar relative proportions and relation of the novel elements, which produce a launcher tube which has successfully obviated the. defects formerly inherent in such launchers. It has been found that satisfactory launching can be secured if the launching tube is designed to aiord an area between the muzzle-brake and the muzzle through which the flow of the gases of the propellant are Substantially eliminated so that there are no disturbing effects of the propellent gases trapped in the tube by the closed breech, when the rocket leaves the muzzle unaiected by any interfering action of Kgases escaping from the muzzle.

While there is disclosed in the drawing and hereinafter fully described one specific embodiment of the invention, it is to be distinctly understood that the invention is not considered to be limited to said specific embodiment but that its scope is defined by the claims appended hereto.

In the drawing:

Fig. 1 is a side elevation of the launcher.

Fig. 2 is a fragmentary, enlarged, vertical section of the tube of the launcher, the rocket in the tube shown in broken lines.

Fig. 3 is an enlarged, vertical section on the line 3 3 of Fig. l, in the direction of the arrows.

Fig. 4 is an enlarged, vertical section on the line 4 5 of Fig. 1, in the direction of the arrows.

Fig. 5 is an enlarged, vertical section on the line 5 5 of Fig. 1, in the direction of the arrows.

As illustrated in the drawing, the launcher has a suitable breech casting I, providing with recoil ways 2, and breech housing 3, for the breech lock (not shown) and into which the tube ll, is threaded. The tube 4, is provided with three guide rails 5, symmetrically disposed at intervals of on the inner periphery of tube d. Each rail 5 consists of a channel which is substantially U-shaped in cross-section and which is provided with lateral base flanges 6 and l. The base ange 6 is attached to the inner face of tube Il as by screws 8, or by lwelding. Plates 'I bear against the inner face of tube d, unattached thereto, to permit slight movement of channels 5 radially of tube d, channels 5 and flanges S and 'I being suciently resilient. Rails 5 are somewhat spaced forwardly of the breech end of tube f3 and have oblique rear end faces 9, forming intake ports I0, for channels 5. Each channel 5 is closed at the muzzle by a plug 5-a. Each channel 5 has an :outlet port Il, opening through the wall of tube 4. Tube 4 is provided with outlet ports I2, two ports I2 being provided in each section of the periphery of tube Ll between ports II. Ports Il and I2 are in the form of longitudinal slots through the wall of tube li, feorming a muzzle-brake for tube il. These slots are of uniform length and slots I2 are substantially twice the `width of slots II. They are spaced from the muzzle not less than one quarter of the length of tube 4, their forward and rear ends lying in comlmon planes transverse to the axis of tube il, respectively.

The tube 4 is provided with an obturating ring I3, disposed forwardly of the ports II and I2. This ring I3 comprises three arcuate members I4 fitted between the rails 5. Each portion I4 has a recess Ill' in which is slidable the flange 1 of one of rails 5. The rear end I5 of the ring I3 is spaced somewhat rearwardly of the forward endsof the ports II and I2. See Figure 1. The ring I3 has a frusto-conical portion I6 divergent from end I5 to the forward ends of ports II and I2. The front end Il of ring I3 is substantially midway between the forward ends of portsv Y tween rails 5.

II and I2 and the muzzle of tube 4. The forward portion IB of ring I3 diverges at an acute angle to the inner surface of tube t.

The above described elements of the launcher are so designed and related that when the'rocketY u R is introduced into the tube 4 through its opened breech, the bourrelets B and B-I of rocket R are receivedon rails 5, which Vresiliently bear thereon, thereby coinciding the axes vof the `rocket R and tube 4. It will be noted that the ner that the rear bourrelet =B,passes forwardly 'Y of the ports II and I2 before the'forward bour relet B-I leaves rails 5 at the muzzle.

The specific embodiment of the invention illustrated in the drawing and hereinbefore fully described is designed for launching a 3.5" Irocket. Successful tests of this launcher have indicated that the correctdimensions are as follows. The tube 4 should measure iifty inches from the breech to the muzzle. The ports II and I?. should be three inches long, land their rearends should be not less than Vfourteen and one-half inches rearwardly of the muzzle. The obtui'ating ring I3 should be six linches long, its vfrusto-conical portion I6 extending into the portsjI I and I2 being one half an inch long, and its vdivergent forward portion I8 being two inches long. The foregoing dimensions providel an area, not less than twelve inches long, in the tube 4 between the rear end of the obturating .ring I3 and the muzzle. f Y

' It is obvious from the foregoing'description of the details of construction ofl the improved launcher that when the propellant of Ythe rocket R is ignited the'gases trapped in tube ilv by its closed breech pass forwardly throughV tuberi begases, due to the closed breech, this gas ow is at Va rate superior to the rate of travel of rocket R.

Because of the pressure of theV longitudinal axes of the tube and aY rocket launched therefrom during the period of travel of the rocket through the tube, said rails constituting conduit means for discharging propellent gases of the rocket from theV breech end of the tube forwardly along said tube.

2. In a rocket launcher, the combination of a tube closed at itsbreech end, andaiplurality of hollow, circumferentially-spaced rocket-guiding rails mounted on the inner surface of said tube `.and extending longitudinally therealong, at least one of said rails comprising a gas conduit having an intake port within said tube adjacent the breech end thereof, there being a discharge port .opening through the Wall of said tube intermediate the ends thereof, and communicating with 1the interiorof said one rail.

R,'their discharge from the muzzle Vdoes not 'Y affect the rocket R. travelling on rails ,5. When the forward end of rocket R reaches the rear Yend of ring I3, a throttling action lis produced by sections I4, causing the major portion of the gases posterior to rocket R to be evacuatedY through discharge ports I2, the ring I3 assisting the discharge. Y

The trapped gases al-so enter channels 5 through intake ports I0 and are evacuated therefromthrough discharge ports II, the forward ends of channels 5 being sealed by plugs S-u. Thus theY portion of the tube 4 forwardly .of the rear end of ring I3, when rocket Rreaches the rear end of ring I3, receives only the negligible amount of the unevacuated gases flowing forwardly in the'spaces 2i] between the inner surfaces S-I of members I4 and the outer wall W of the rocket R. (Fig. 4). Due to the divergence of portion Iii of ring I3, this `amountof the gases is considerably expanded forwardly of ring I3 reducing the pressure sufficiently to render the unevacuated gases innocuous when discharged from the muzzle.

Having described `the invention, what I claim is:

11. In a rocket launcher, the combination of a launching tube closed Vat its breech and hollow lportion I B of 3. In a rocket launcher, the combination of a tube having its breech end gas tight, more than two, uniformly circumferentially spaced rocketguiding rails mounted on the inner surface of thetube and,extendinglongitudinally therea-lpng; Y

an obturatingring comprising a pllllfltvof arcuf ate' circumferentially extending members ,mount-ied on the inner surface ofthe tubeEbetween said rails'there being a slot throughfthe ,wall of `said tube immediately rearwardly of said ring.

4. In a rocket launcher, the combination 0f Aa tube having a closed breech and@ ,5.1012 QQmprSiBg a muzzle-brake, said slot being located.;?.il2Iu-o.xi. mately one-quarter of the length of .said tube from its muzzle end, a plurality of lroc.keit-.guiding rails mounted on the inner surface Uof :the -.tube, each of said rails comprising a gasconduit hav..- ing an intake port adjacent the :breech ,end of said tube, and a discharge lport,through the wail of said tube and in the same transverse plane `as said slot, and an obturating .ring comprising a plurality of arcuate members Amounted onthe inner surface of the tube between the rails, :the rearward end of said ring lying -in .said plane.

Y 5. In a rocket launcher, vthe .combination of .a tube having a closed breech; a plurality of .cire cumferentially spaced resilient .rocket-.guiding rails extending longitudinally .of said tube, each of said rails being substantially Urshapcd .incross section and provided with lateral .outwardly ex.- tending anges, one said flange being :fixed tothe inner face of said tube, and the other .being in slidable contact thereon; and an obturatingring Vcomprising a plurality of arcuate members mounted on the inner surface ofthe tube rbetween the rails there being at least .one slot through the wall of `said tube immediately rearwardly of .s aid ring.

6,. In a rocket launcher, the `combination of a tube having a closed breech, a plurality Aof rocketguiding `rails mounted on the innerY surface of said tube, each rail comprising a gas duct having an inlet port communicating with the interior of said tube adjacent its breech end/there being slots through the wall of said tube, said slots being located approximately one-fourth length of said tube from the muzzle end thereof, each slot communicating with the `interior pf t a respective rail to form a gas discharge port, there also beingV slots through the wall ,of said tube between saidV rails, Ysubstantially in :the san-le transverse plane with said rstfnamed slots, ,and obturating ring means in said tube just forwardly Y of said slots.V

'7. In a rocket launcher, the .combi-nation ,of a tube having a closed breech and a .plurality of hollow rails circumferentially spaced about the inner surface of said tube to engage and guide a rocket for translation therealong, the ends of said rails adjacent the breech of said tube being open, there being a port through the Wall of said tube to the interior of each rail, there being additional ports through the Wall of said tube to the interior thereof, all said ports being approximately one-fourth the length of said tube from the muzzle thereof, and obturating ring means in said tube just forwardly of said ports, said ring means comprising arcuate sections secured to said tube wall between said rails and forming a gas tight t with a rocket guided on said rails.

ADEN B. MEINEL.

REFERENCES CITED The following references are of record in the le of this patent:

UNITED STATES PATENTS Number Name Date 2,426,610 Hopkins Sept. 2, 1947 2,430,636 Gould NOV. 11, 1947 FOREIGN PATENTS Number Country Date 126,336 Great Britain May 15, 1919 468,583 Great Britain July 8, 1937 611,075 France June 26J 1926 

